EP3719332A1 - Lagergehäuse mit flexiblem gelenk - Google Patents

Lagergehäuse mit flexiblem gelenk Download PDF

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Publication number
EP3719332A1
EP3719332A1 EP20166768.0A EP20166768A EP3719332A1 EP 3719332 A1 EP3719332 A1 EP 3719332A1 EP 20166768 A EP20166768 A EP 20166768A EP 3719332 A1 EP3719332 A1 EP 3719332A1
Authority
EP
European Patent Office
Prior art keywords
bearings
case
central axis
gas turbine
turbine engine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP20166768.0A
Other languages
English (en)
French (fr)
Other versions
EP3719332B1 (de
Inventor
Guy Lefebvre
Remy Synnott
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Pratt and Whitney Canada Corp
Original Assignee
Pratt and Whitney Canada Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Pratt and Whitney Canada Corp filed Critical Pratt and Whitney Canada Corp
Publication of EP3719332A1 publication Critical patent/EP3719332A1/de
Application granted granted Critical
Publication of EP3719332B1 publication Critical patent/EP3719332B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C19/00—Bearings with rolling contact, for exclusively rotary movement
    • F16C19/54—Systems consisting of a plurality of bearings with rolling friction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • F01D25/164—Flexible supports; Vibration damping means associated with the bearing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/06—Arrangements of bearings; Lubricating
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C27/00—Elastic or yielding bearings or bearing supports, for exclusively rotary movement
    • F16C27/04—Ball or roller bearings, e.g. with resilient rolling bodies
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
    • F16C33/30—Parts of ball or roller bearings
    • F16C33/66—Special parts or details in view of lubrication
    • F16C33/6637—Special parts or details in view of lubrication with liquid lubricant
    • F16C33/6685—Details of collecting or draining, e.g. returning the liquid to a sump
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/027—Arrangements for balancing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/50—Bearings
    • F05D2240/54—Radial bearings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/90—Mounting on supporting structures or systems
    • F05D2240/91—Mounting on supporting structures or systems on a stationary structure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/15—Load balancing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • F05D2260/609—Deoiling or demisting
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/98—Lubrication
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C19/00—Bearings with rolling contact, for exclusively rotary movement
    • F16C19/02—Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows
    • F16C19/14—Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for both radial and axial load
    • F16C19/16—Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for both radial and axial load with a single row of balls
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2240/00—Specified values or numerical ranges of parameters; Relations between them
    • F16C2240/30—Angles, e.g. inclinations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2360/00—Engines or pumps
    • F16C2360/23—Gas turbine engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
    • F16C33/30—Parts of ball or roller bearings
    • F16C33/66—Special parts or details in view of lubrication
    • F16C33/6637—Special parts or details in view of lubrication with liquid lubricant
    • F16C33/6659—Details of supply of the liquid to the bearing, e.g. passages or nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C35/00—Rigid support of bearing units; Housings, e.g. caps, covers
    • F16C35/04—Rigid support of bearing units; Housings, e.g. caps, covers in the case of ball or roller bearings
    • F16C35/042—Housings for rolling element bearings for rotary movement

Definitions

  • the application relates generally to gas turbine engines and, more particularly, to bearing housing assemblies used in such engines.
  • a rotary shaft holding compressor/fan and turbine blades is rotatably mounted within a casing via bearings.
  • the bearings are typically located radially inwards relative to the annular flow path formed by duct walls of the casing.
  • a bearing housing usually encloses the bearings and defines a bearing cavity for receiving lubricant for lubricating the bearings. Due to the forces inherent to gas turbine engine operation, and as they are the interface between shafts and a support structure, the bearings are exposed to loads, vibrations, etc that may affect their performance over time.
  • a gas turbine engine comprising a bearing housing having at least two bearings axially spaced from one another relative to a central axis, the bearing housing having a case between the at least two bearings having a joint configured for relative axial movement between the bearing supports.
  • the bearing housing comprises at least two bearing supports, each bearing support engaging a corresponding bearing.
  • a gas turbine engine comprising a shaft rotatable about a central axis, the shaft supported by at least two bearings supported by a common bearing housing, the bearing housing having a case including an elbow section located between the at least two bearings forming a joint allowing relative axial movement between the bearing supports.
  • a method of operating a bearing assembly for a gas turbine engine comprising: supporting at least two bearings being axially spaced apart relative to a central axis; receiving a first axial load at least at one of the at least two bearings and receiving a second axial load greater than the first axial load at the other of the at least two of the bearings; and bending a case interconnecting the at least two bearings to axially move the at least two bearings relative to one another relative to the central axis as a result of a difference between the first axial load and the second axial load.
  • Fig. 1 illustrates a gas turbine engine 10 of a type preferably provided for use in subsonic flight, generally comprising in serial flow communication a fan 12 through which ambient air is propelled, a compressor section 14 for pressurizing the air, a combustor 16 in which the compressed air is mixed with fuel and ignited for generating an annular stream of hot combustion gases, and a turbine section 18 for extracting energy from the combustion gases.
  • the fan 12, the compressor section 14, and the turbine section 18 are rotatable about a central axis 11.
  • the compressor section 14, fan 12 and turbine section 18 have rotating components which can be mounted on one or more shafts 20, 22, which, in this embodiment, rotate concentrically around the central axis 11.
  • Bearings 24 are used to provide smooth relative rotation between a shaft (20 or 22) and casings 26, 28 ( Fig. 2 ) (non-rotating component), and/or between the two shafts 20, 22 which rotate at different speeds.
  • FIG. 2 a cross-sectional view of a portion of the turbine section 18 is illustrated.
  • a bearing assembly is generally shown at 100.
  • the bearing assembly 100 is located radially inwardly of vanes 18a of the turbine section 18 relative to the central axis 11.
  • the bearing assembly 100 includes bearings 110 and a bearing housing 120 enclosing the bearings 110.
  • the bearing housing 120 is used for defining a bearing cavity C circumferentially extending around the axis 11.
  • the bearing cavity C is used for receiving lubricant from a lubrication system S for lubricating the bearings 110.
  • the bearing 110 and the bearing housing 120 are described in succession herein below.
  • two bearings 110 are shown and are axially offset from each other relative to the central axis 11. It is understood that the gas turbine engine 10 may include more than two bearings. For the sake of clarity, only one of the two bearings 110 is described herein below using the singular form, but the description may apply to both of the bearings 110.
  • the bearing 110 is used to allow a rotation of the shaft 20 relative to the bearing housing 120 and to substantially maintain a radial position of the shaft 20 relative to the casing 28 of the gas turbine engine 10.
  • the bearing 110 may include an inner race 112 secured to the shaft 20, an outer race 114 secured to the bearing housing 120 and/or rolling elements 116 located radially between the inner and outer races 112, 114.
  • the rolling elements 116 may be spherically, cylindrically, frustoconically shaped, among examples. Any suitable bearing known in the art may be used.
  • the shaft 20 may rotate at a relatively high speed relative to the casing 28, proper lubrication of the bearings 110 may be required.
  • the lubrication system S injects the lubricant within the bearing cavity C. It might be desirable to keep the lubricant within the bearing cavity C. This function may be carried by the bearing housing 120 and sealing members (not shown).
  • the bearing housing 120 includes a case 122 that circumferentially extends all around the central axis 11.
  • the case 122 extends at least axially relative to the axis 11 and may span a distance between the two bearings 110.
  • Two bearing supports 124 are secured at axial extremities of the case 122. Each of the two bearing supports 124 is in engagement with a respective one of the outer races 114 of the bearings 110.
  • the two bearing supports 124 are stiffer than the case to be able to withstand loads applied thereto from the shaft 22 via the bearing 110. In the embodiment shown, a radial thickness of the two bearing supports 124 is greater than that of the case 122.
  • the bearings 110, and the bearing supports 124 may be spaced apart by an axial distance greater than a diameter of the shaft 22. As shown, the axial distance between the two bearing supports 124 is greater than a chord length of the vanes 18a of the turbine section 18.
  • the bearing housing 120 further includes securing members 126 for attaching the bearing housing 120 to the casing 28 of the gas turbine engine 10.
  • the securing members 126 are flanges, also referred to as hairpins, 128 extending radially outwardly from the case 122.
  • the flanges 128 may extend circumferentially all around the central axis 11.
  • the flanges 128 may be annular walls.
  • Securing members 126 may have other configurations, such as tabs, non-flange annular walls, an annular bracket, etc.
  • the securing members 126 are configured to be secured to connecting members 28a extending radially inwardly from the casing 28.
  • fasteners are used to secure the securing members 126 (e.g., the flanges 128) to the connecting members 28a of the engine casing 28.
  • Other fixation means are contemplated.
  • each of the securing members 126 is axially aligned with a respective one of the bearing supports 124.
  • the flanges 128 extend radially outwardly from the bearing supports 124 relative to the central axis 11.
  • each of the flanges 128 is securable to a respective one of the connecting members 28a of the casing 28.
  • Interfaces I between the flanges 128a and the connecting members 28a are located on sides of the flanges 128a that face axially rearward relative to the central axis 11. This might allow to insert the bearing housing 120 within the casing 28 in an axial direction relative to the central axis 11.
  • the stiffness of the two bearing supports 124 of the bearing housing 120 it might be advantageous to vary the stiffness of the two bearing supports 124 of the bearing housing 120.
  • increasing the stiffness of one of the two bearing supports 124 may indirectly increase that of the other.
  • the two bearing supports 124 of the bearing housing 120 vary in their respective stiffness, they might react differently to temperature variations.
  • the bearing housing 120 is installed in the turbine section 18, one of the two bearing supports 124 might subjected to different thermal expansion than the other which might include thermal stresses. This phenomenon may be enhanced by the high temperature gradients in the turbine section 18. More specifically, the casing 28 might be more affected to the temperature of exhaust gases circulating in the turbine section 18 than the bearing housing 120 as the casing 28 is closer to the exhaust gases. This might create thermal stress.
  • the case 122 of the bearing housing 120 includes an elbow or joint 132 that allows relative axial movement between the bearing supports 124 and between the bearings 110.
  • the case 122 is axisymmetric relative to the central axis 11, though the case 122 may not be axisymmetric.
  • the case is made of flexible sheet metal.
  • the joint 132 may be defined by a kink 134 in the case 122.
  • the kink 134 is created by an intersection of two generally continuous case sections 122a that are joined together at the kink 134 - in the context that the case 122 may be a monolithic piece.
  • the case sections 122a may be frustoconical.
  • Each of the two case sections 122a extends from a respective one of the bearing supports 124 toward the other of the bearing supports 124.
  • the two case sections 122a define an angle ⁇ at the kink 134.
  • the angle ⁇ between the two case sections 122a is variable to allow the axial movements between the at least two bearings 110.
  • the angle ⁇ is oriented radially inward and is obtuse. In an embodiment, the angle ⁇ is greater than 90 degrees and less than 170 degrees.
  • the kink 34 may be referred to as a bend, a deflection, etc.
  • the joint 132 is located at a radially-outward most location of the case 122.
  • the joint 132 is able to move radially inwardly toward the central axis with an increase of the angle ⁇ and with an increase of an axial distance relative to the central axis 11 between the two bearings 110. Stated differently, the case 122 is getting straighter when the axial distance between the two bearings 110 increases.
  • the bearing supports 124 might be able to directly transfer radial loads from one of the bearings 110 to the casing 28 of the gas turbine engine 10 without transferring said radial loads to the other of the bearings 110.
  • the case 122 defines apertures 122b configured for receiving bosses 136.
  • the apertures 122b are circumferentially equidistantly distributed about the central axis 11. Stated otherwise, a circumferential distance taken along the central axis between two adjacent ones of the apertures 122b and of the bosses 136 is constant.
  • the case 122 is axisymmetric with the bosses 136a, 136b, 136c.
  • the bosses and apertures are spaced apart from one another by 120 degrees.
  • the bosses 136 may be welded on the case 122.
  • three apertures 122b are defined through the case 122; each of the three apertures 122b being engaged by a respective one of an oil feed boss 136a, an oil scavenging boss 136b, and a non-functional boss 136c.
  • the non-functional boss 136c is merely a piece of metal and might not connected to any other component of the engine 10.
  • the non-functional boss 136c may be used to even the stress distribution by maintaining an axisymmetric architecture. In other words, a weight distribution on the bearing housing 120 may be axisymmetric because of the non-functional boss 136c.
  • the oil scavenging boss 136b is located at a lower portion of the case 122 such that lubricant may flow naturally by gravity toward the oil scavenging boss 136b and the corresponding one of the apertures 122b.
  • the two case sections 122a slope radially outwardly toward the joint 132.
  • the oil scavenging boss 136b may be located proximate to the joint 132 such that oil flows naturally against the case sections 122a toward the oil scavenging boss 136b by gravity.
  • a first axial load is received at least at one of the at least two bearings 110 and a second axial load greater than the first axial load is received at the other of the at least two of the bearings; the case is bent to axially move the at least two bearings relative to one another relative to the central axis as a result of a difference between the first axial load and the second axial load.
  • bending the case 122 includes moving the joint 132 connecting the two case sections 122a of the case toward the central axis 11.
  • the disclosed bearing housing 120 might allow for an axial thermal displacement in relation to the casing 28 of the engine 10.
  • the disclosed housing 120 allows for a dual bearing housing hairpin connection that support at least two bearings 110 in a single housing 120. Having the bosses 136 evenly distributed might allow for an uniform stress distribution all around the bearing housing 120.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Rolling Contact Bearings (AREA)
  • Sliding-Contact Bearings (AREA)
  • Mounting Of Bearings Or Others (AREA)
EP20166768.0A 2019-03-29 2020-03-30 Lagergehäuse mit flexiblem gelenk Active EP3719332B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US16/369,632 US10808573B1 (en) 2019-03-29 2019-03-29 Bearing housing with flexible joint

Publications (2)

Publication Number Publication Date
EP3719332A1 true EP3719332A1 (de) 2020-10-07
EP3719332B1 EP3719332B1 (de) 2021-11-24

Family

ID=70058251

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20166768.0A Active EP3719332B1 (de) 2019-03-29 2020-03-30 Lagergehäuse mit flexiblem gelenk

Country Status (3)

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US (1) US10808573B1 (de)
EP (1) EP3719332B1 (de)
CA (1) CA3074857A1 (de)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11492926B2 (en) 2020-12-17 2022-11-08 Pratt & Whitney Canada Corp. Bearing housing with slip joint
JP7352590B2 (ja) * 2021-04-02 2023-09-28 三菱重工業株式会社 ガスタービン

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EP2192276A2 (de) * 2008-11-28 2010-06-02 Pratt & Whitney Canada Corp. Mittelturbinenrahmen einer Gasturbine

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CA3074857A1 (en) 2020-09-29
US10808573B1 (en) 2020-10-20
US20200308982A1 (en) 2020-10-01
EP3719332B1 (de) 2021-11-24

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